A hydraulic actuator system 1 is provided for driving a movable portion attached to a wing 5 of an airplane. A plurality of first system hydraulic actuators 2 and a plurality of second system hydraulic actuators 3 are included and are connected to the movable portion. The first system hydraulic actuators 2 are attached to the wing 5 and connected to a first hydraulic pressure source, whereas the second system hydraulic actuators 3 are attached to the wing to be in parallel to the first system hydraulic actuators 2 and are connected to a second hydraulic pressure source. The first system hydraulic actuators 2 and the second system hydraulic actuators 3 are alternately provided at a predetermined part of the wing 5.


    Access

    Download


    Export, share and cite



    Title :

    Hydraulic actuator system for aircraft


    Additional title:

    Hydraulisches Aktuatorsystem für Flugzeuge
    Système d'actionneur hydraulique pour aéronefs


    Contributors:
    SUZUKI KAZUYUKI (author) / ITOH KOJI (author)

    Publication date :

    2017-08-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Aircraft actuator hydraulic system

    FUKUI ATSUSHI / TAKAGI NORIMASA | European Patent Office | 2018

    Free access

    Aircraft actuator hydraulic system

    FUKUI ATSUSHI | European Patent Office | 2018

    Free access

    Aircraft actuator hydraulic system

    FUKUI ATSUSHI | European Patent Office | 2019

    Free access

    HYDRAULIC SYSTEM OF AIRCRAFT ACTUATOR

    FUKUI ATSUSHI / TAKEDA MINORU | European Patent Office | 2016

    Free access

    ELECTRIC HYDRAULIC PRESSURE ACTUATOR FOR AIRCRAFT

    SATO KOSUKE / OGAWA YOSHIYUKI / ONO FUMIAKI et al. | European Patent Office | 2019

    Free access